Ultrafast-response green pollution-free light-operated solid propellant and preparation method thereof

Abstract

The invention belongs to the field of laser ignition and propulsion, and particularly relates to an ultrafast-response green pollution-free light-operated solid propellant and a preparation method thereof. Comprising the following components in percentage by mass: 10-15% of pentaamino tetrazole serving as a gas generating agent, 75-85% of a mixture of ammonium dinitramide and ammonium nitrate serving as an oxidizing agent, 2-4% of infrared dye serving as a light absorbing agent and 5% of a mixture of glycidyl azide polymer and phenolic resin serving as a binding agent. All the raw material components are fully mixed and then pressed through an oil press, and the propellant grain required by an experiment is prepared. The light-operated solid propellant prepared by the invention successfully realizes accurate light control, the ignition delay time is 5-55ms, and the flameout delay time is 5-13ms. Green and environment-friendly agents ADN and AN are selected as oxidants, compared with traditional toxic and harmful oxidants, the propellant does not generate a large number of solid particles and high-temperature gas, pollution to the environment and harm to human health are greatly reduced in the using process, and therefore the propellant has good application prospects.

Description

Technical Field

[0001] The invention relates to an ultrafast-response green and pollution-free light-controlled solid propellant, belonging to the field of laser ignition and propulsion. Background Art

[0002] Laser ignition technology utilizes a high-energy laser beam focused on a localized area, triggering an ignition and combustion reaction through thermal effects. This technology offers advantages such as high energy density, high precision, and contactless triggering, making it widely used in aerospace, energy, and military fields. However, conventional self-sustaining combustion propellants continue to burn even after the ignition energy is removed, making it difficult to precisely control the attitude and trajectory of a spacecraft. In contrast, ultrafast-response light-controlled solid propellants enable precise on-off control of the combustion state: instantaneous ignition upon laser incidence provides thrust, and the flame quickly extinguishes after the laser is turned off. Their millisecond-level ignition / extinguishing delay significantly enhances precision control capabilities for applications such as deep space exploration and missile propulsion. However, conventional solid propellants pose environmental pollution risks, producing large amounts of harmful exhaust gases and solid residues during combustion. Green light-controlled propellants, through their non-self-sustaining combustion characteristics and combined with an environmentally friendly oxidizer system, can significantly reduce pollutant emissions and avoid the negative impact of contamination on the optical path. Currently used solid propellants have limitations in response speed, pollution control, and shutoff capabilities, making them difficult to meet the high-precision attitude and trajectory adjustment requirements of modern spacecraft. Therefore, the development of new solid propellant with ultrafast response, environmental friendliness and controllable combustion characteristics has become an urgent technical need in the field of aerospace propulsion. Summary of the Invention

[0003] The present invention aims to provide an ultrafast-response, green, pollution-free, light-controlled solid propellant. The propellant comprises the following components by weight: 10% to 15% gas generator, 75% to 85% oxidizer, 2% to 4% light absorber, and 5% binder. Experimental testing has shown that the solid propellant has an absorptivity of 90-95% at 982 nm. The propellant has a density of 1.4-1.6 g / cm². 3 , cylindrical charge with a diameter of 6mm and a length of 10mm. When the spot diameter is 6mm, the laser power density is 0.25~2.4W / mm 2 Within this range, the solid propellant can successfully ignite and achieve light control, and has extremely short ignition delay and flameout delay. The ignition delay time is 10 to 55 ms, and the flameout delay time is 5 to 13 ms, which can achieve more precise attitude control and positioning, thereby improving the navigation and positioning accuracy of the spacecraft. Secondly, the present invention selects green and environmentally friendly agents ADN and AN as oxidants. Compared with traditional toxic and harmful oxidants, the solid propellant does not produce a large amount of solid particles and high-temperature gases, and the pollution to the environment and the harm to human health during use are greatly reduced. Therefore, it has good application prospects and can solve the shortcomings of existing propellants.

[0004] The technical solution of the present invention is: an ultrafast response green and pollution-free light-controlled solid propellant, whose raw materials include the following components by mass fraction: 10% to 15% of a gas generating agent, 75% to 85% of an oxidizing agent, 2% to 4% of a light absorber, and 5% of a binder.

[0005] Furthermore, the oxidant used is a mixture of the environmentally friendly oxidants ammonium dinitramide (ADN) and ammonium nitrate (AN) in a 1:1 mass ratio. Because the combustion products of ADN and AN are primarily nitrogen, water, and some oxides, they have lower toxicity and higher thermal stability compared to traditional toxic and hazardous oxidants.

[0006] Furthermore, the fuel uses pentaaminotetrazole (5-ATZ), which provides more gaseous combustion products to the propellant, thereby improving the combustion performance and propulsion performance of the propellant.

[0007] Furthermore, the light absorber is one or more infrared dyes to ensure that the solid propellant has good absorption performance for laser light in the 982nm band.

[0008] Furthermore, the binder is a mixture of glycidyl polyazide (GAP) and phenolic resin (PF) in a mass ratio of 3:2. GAP is an energetic binder that ensures the mechanical properties and overload resistance of the propellant while also ensuring its combustion performance.

[0009] The preparation method of the above-mentioned solid propellant comprises the following steps:

[0010] S1. Sphericalizing the ADN raw material.

[0011] S2. Oven-dry the raw materials, ball-mill and vibrate-screen the gas generator and oxidant to obtain reagents of different particle sizes, and mix the gas generator, oxidant, and light absorber according to the ratio and grind them.

[0012] S3. Add the binder mixture gradually to the uniform powder obtained in S1 and stir evenly.

[0013] S4. Use a hydraulic press to compress the agent described in S3 to obtain a propellant grain, dry the propellant grain, and place it in a fixture for laser ignition.

[0014] Furthermore, in S2, the gas generating agent 5-ATZ is screened using a sieve frame with a mesh size greater than 300 mesh; the oxidizing agent ADN is screened using a sieve frame with a mesh size range of 160 mesh to 240 mesh.

[0015] Furthermore, in S4, the pressing pressure is selected to be 50 MPa, the room temperature is controlled to be 25° C., and the air humidity is lower than 40%.

[0016] The present invention provides an application of an ultrafast-response green and pollution-free light-controlled solid propellant, characterized in that it is ignited by laser, and the laser power density range is 0.25 to 2.4 W / mm 2 .

[0017] Compared with the prior art, the present invention has the following advantages:

[0018] (1) The gel propellant successfully achieves light control and has a shorter response time, more precise attitude control and positioning capabilities, thereby improving the navigation and positioning accuracy of the spacecraft.

[0019] (2) The 982nm band has good laser absorption performance, which can effectively utilize laser energy and thus improve energy utilization.

[0020] (3) The solid propellant uses green and environmentally friendly agents ADN and AN as oxidants. Compared with traditional toxic and harmful oxidants, the propellant does not produce a large amount of solid particles and high-temperature gas, and the pollution to the light path during use is greatly reduced.

[0021] (4) After experimental testing, the absorption rate of the solid propellant in the 982nm band is 90-95%. The density of the propellant is 1.4-1.6g / cm 3 , cylindrical charge with a diameter of 6mm and a length of 10mm. When the spot diameter is 6mm, the laser power density is 0.25~2.4W / mm 2 Within this range, the solid propellant can successfully ignite and achieve light control with extremely short ignition and flameout delays. The ignition delay time is 5 to 55ms, and the flameout delay time is 5 to 13ms. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a production process flow chart of the ultrafast-response, green, pollution-free, light-controlled solid propellant of the present invention.

[0023] Figure 2 This is a diagram of the ignition experiment of different light absorbers of the ultrafast response green and pollution-free light-controlled solid propellant of the present invention. DETAILED DESCRIPTION

[0024] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0025] Example 1:

[0026] like Figure 1According to the solid propellant preparation process, ADN is first spheroidized to obtain raw materials. The raw materials are oven-dried, and the gas generator and oxidizer are ball-milled and sieved to obtain the required particle size. The corresponding mass of ADN, AN, 5-ATZ, and infrared dye are weighed, mixed, and then ground. The binder mixture is added gradually to the obtained uniform powder and stirred evenly. The agent described in S3 is pressed using an oil press to obtain a propellant pellet with a diameter of 6 mm and a length of 10 mm. The propellant pellet is dried and placed in a fixture for laser ignition. The corresponding performance parameters are tested under the conditions of a laser power of 7 W and a spot diameter of 6 mm.

[0027] Table 1 Solid propellant formulations and corresponding performance parameters of Example 1

[0028]

[0029] Example 2:

[0030] Other parameters are the same as those in Example 1, except that the laser power density is changed. The performance parameters are shown in Table 2.

[0031] Table 2 Solid propellant formulations and corresponding performance parameters of Example 2

[0032]

[0033]

[0034] Example 3:

[0035] Other parameters are the same as those in Example 1, except that the laser power density is changed. The performance parameters are shown in Table 3.

[0036] Table 3 Solid propellant formulations and corresponding performance parameters of Example 3

[0037]

[0038] Example 4:

[0039] Other parameters are the same as those in Example 1, except that the laser power density is changed. The performance parameters are shown in Table 4.

[0040] Table 4 Solid propellant formulations and corresponding performance parameters of Example 4

[0041]

[0042] Example 5:

[0043] Other parameters are the same as those in Example 1, except that the laser power density is changed. The performance parameters are shown in Table 5.

[0044] Table 5 Solid propellant formulations and corresponding performance parameters of Example 5

[0045]

[0046] Example 6:

[0047] Other than Example 1, change laser power density, performance parameters see Table 6.

[0048] Table 6. Solid propellant formulation of Example 6 and corresponding performance parameters

[0049]

[0050]

[0051] Example 7:

[0052] Other than Example 1, change laser power density, performance parameters see Table 7.

[0053] Table 7. Solid propellant formulation of Example 7 and corresponding performance parameters

[0054]

[0055] Example 8:

[0056] Other than Example 2, change light absorber infrared dye type, performance parameters see Table 8.

[0057] Table 8. Solid propellant formulation of Example 8 and corresponding performance parameters

[0058]

[0059] Example 9:

[0060] Other than Example 3, change light absorber infrared dye type, performance parameters see Table 9.

[0061] Table 9. Solid propellant formulation of Example 7 and corresponding performance parameters

[0062]

[0063] Comparative Example 1:

[0064] Find other related light-controlled solid propellant solid propellant performance parameters made of solid propellant, under the condition of optimal ignition and extinction delay time, other light-controlled solid propellant performance parameters see Table 10.

[0065] Table 10. Nitroguanidine-based light-controlled solid propellant and corresponding performance parameters

[0066]

[0067]

[0068] Comparative Example 2:

[0069] Table 11 ADN-based light-controlled solid propellants and corresponding performance parameters

[0070]

[0071] Comparative Example 3:

[0072] Table 12 ADN-based light-controlled gel propellants and corresponding performance parameters

[0073]

[0074] Comparative Example 4:

[0075] Table 13 AP / AN based light-controlled solid propellants and their corresponding performance parameters

[0076]

[0077] Comparative Example 5:

[0078] Solid propellant formulation of Example 14 and corresponding performance parameters

[0079]

[0080]

[0081] Comparative Example 6:

[0082] Solid propellant formulation of Example 15 and corresponding performance parameters

[0083]

[0084] In summary, in Examples 1-7, the gas generating agent 5-ATZ 12%, the oxidant ADN 40%, AN 40%, the light absorber 3%, the binder polyazide glycidyl ether (GAP) and phenolic resin (PF) in a mass ratio of 3:2 is 5%, and the propellant ignition delay time is shortened with the increase of laser power density. In Examples 8-9, the type of infrared dye is changed to IR1001. Under the same laser power density conditions, the ignition delay time of IR1001 is slightly longer than that of IR1036. In Comparative Examples 1-4, other system light-controlled solid propellants are compared, and their ignition delay times are all longer than the solid propellant of the present invention. In Comparative Example 5, the solid propellant without the addition of the light absorber is difficult to ignite, and the ignition delay time is greatly increased to 6000ms. In Comparative Example 6, the laser power density is less than 0.25W / mm 2 , the propellant cannot ignite.

[0085] The spot diameter is 6mm, and the laser power density is 0.25~2.4W / mm 2 Within this range, the solid propellant can successfully ignite and achieve light control, and has extremely short ignition delay and flameout delay. The ignition delay time is 5 to 55ms, and the flameout delay time is 5 to 13ms, which can achieve more precise attitude control and positioning, thereby improving the navigation and positioning accuracy of the spacecraft. Secondly, the present invention selects green and environmentally friendly agents ADN and AN as oxidants. Compared with traditional toxic and harmful oxidants, the solid propellant does not produce a large amount of solid particles and high-temperature gases, and the pollution to the environment and the harm to human health during use are greatly reduced. Therefore, it has good application prospects and can solve the shortcomings of existing propellants.

[0086] The above embodiments are generally applicable and their description is relatively specific and detailed, but they should not be construed as limiting the scope of the present invention. Any simple modification, modification, or equivalent variation of the above embodiments based on the essence of the present invention falls within the scope of protection of the technical solution of the present invention.

Claims

1. An ultrafast-response, green, pollution-free, light-controlled solid propellant, characterized by: The invention comprises the following components by mass fraction: 10% to 15% of a gas generating agent, 75% to 85% of an oxidizing agent, 2% to 4% of a light absorber and 5% of a binder.

2. The light-controlled solid propellant according to claim 1, characterized in that: Pentaaminotetrazole is used as the gas generating agent.

3. The light-controlled solid propellant according to claim 1, characterized in that: The oxidant is a mixture of green and environmentally friendly oxidants ADN and AN in a mass ratio of 1:

1.

4. The light-controlled solid propellant according to claim 1, characterized in that: The light absorber is one or more infrared dyes.

5. The light-controlled solid propellant according to claim 1, characterized in that: The binder is a mixture of polyazide glycidyl ether and phenolic resin in a mass ratio of 3:

2.

6. The light-controlled solid propellant according to claim 1, characterized in that: Pentaaminotetrazole 10% to 15%, oxidant: mixture of ammonium dinitramide and ammonium nitrate 75% to 85%, light absorber: infrared dye 2% to 4%, binder: mixture of polyazide glycidyl ether and phenolic resin 5%.

7. A method for preparing the ultrafast response green and pollution-free light-controlled solid propellant according to any one of claims 1 to 6, characterized in that: The specific steps include: S1. Sphericalizing the ADN raw material; S2. The raw materials are oven-dried, the gas generating agent and the oxidant are ball-milled and sieved to obtain agents of different particle sizes, and the gas generating agent, the oxidant and the light absorber are mixed and ground according to the ratio; S3. The binder mixture is gradually added to the uniform powder obtained in S1 and stirred evenly; S4. Use a hydraulic press to compress the agent described in S3 to obtain a propellant grain, dry the propellant grain, and place it in a fixture for laser ignition.

8. The preparation method according to claim 7, wherein In S2, the gas generating agent 5-ATZ is screened using a sieve frame with a mesh size greater than 300 mesh; the oxidizing agent ADN is screened using a sieve frame with a mesh size range of 160 mesh to 240 mesh.

9. The preparation method according to claim 7, wherein In S4, the pressing pressure is selected to be 50 MPa, the room temperature is controlled to be 25° C., and the air humidity is lower than 40%.

10. An application of the ultrafast response green and pollution-free light-controlled solid propellant according to any one of claims 1 to 6, characterized in that: The propellant is ignited by laser, with a laser power density ranging from 0.25 to 2.4 W / mm 2 .

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